Tubular Equivalent Regression Rate in Hybrid Rockets with Complex Geometries-Reference-Cited by-同舟云学术

Tubular Equivalent Regression Rate in Hybrid Rockets with Complex Geometries

Published:2019 Issue:4 Volume:17 Page:544-551
ISSN:1884-0485
Container-title:TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN
language:en
Short-container-title:AEROSPACE TECHNOLOGY JAPAN

Author:

KAMPS Landon¹,NAGATA Harunori²

Affiliation:

1. Department of Mechanical and Space Engineering, Hokkaido University

2. Faculty of Engineering, Hokkaido University

Publisher

Japan Society for Aeronautical and Space Sciences

Link

https://www.jstage.jst.go.jp/article/tastj/17/4/17_17.544/_pdf

Reference10 articles.

1. 1) Cecil, O. and Majdalani, J.: Several hybrid rocket technologies hit advanced test stages, Aerospace America, 11 (2016), pp. 54

2. 2) Altman, D. and Holzman, A.: Overview and History of Hybrid Rocket Propulsion, Fundamentals of Hybrid Rocket Combustion and Propulsion, Progress in Astronautics and Aeronautics Vol. 218, Reston, 2007, pp. 1-33.

3. 3) Sutton, G. P. and Biblarz, O.: Hybrid Propellant Rockets, Rocket Propulsion Elements (8^th ed.), John Wiley & Sons, New Jersey, 2010, pp. 594-621.

4. 4) Karp, A. C., Nakazono, B., Manrique, J. B., Shotwell, R., Vaughan, D., and Story, G. T.: A Hybrid Mars Ascent Vehicle Concept for Low Temperature Storage and Operation, AIAA Paper 2016-4962, 2016.

5. 5) Farias, E., Redmond, M., Karp, A. C., Shotwell, R., Mechentel, F. S., and Story, G. T.: Thermal Cycling for Development of Hybrid Fuel for a Notional Mars Ascent Vehicle, AIAA Paper 2016-4563, 2016.

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